Exhaust dissipator/disrupter device

Abstract

A dissipator device comprises a container having an inlet for connection to a rocket exhaust and a plurality of exhaust orifices of smaller dimensions than the inlet for exhaust flow out of the container in a plurality of different directions. A deflector member is positioned in the container in alignment with the inlet in the path of incoming exhaust gases for deflecting the flow. A disrupter member is positioned between the inlet and deflector member, and has a through bore defining an orifice of area less than the exhaust flow area at the plane of the disrupter member, so that exhaust gases flow both through and around the disrupter member, substantially reducing the downstream pressure and impingement heat transfer.

I claim: 
     
       1. A dissipator device for connection to a rocket exhaust, comprising: a container having an inlet at an intermediate point in its length for connection to a rocket exhaust and a plurality of outlet exhaust orifices of smaller dimensions than the inlet for exhaust flow out of the container in a plurality of different directions;   a solid deflector surface in the container opposite the inlet for deflecting incoming exhaust flow out of the incoming flow direction and into deflected flow directions generally normal to the incoming flow direction; and   disrupter means in the container in the path of incoming exhaust flow between the inlet and the deflector surface for reducing the pressure of exhaust gases downstream of the disrupter means, the disrupter means comprising a disrupter member spaced from the inlet having a through bore aligned with the inlet, the through bore having an inlet opening at one end positioned closest to the inlet of an area less than the cross-sectional area of the exhaust flow at the inlet opening and shaped for restricting the exhaust gas flow and directing it through and around the disrupter member.   
     
     
       2. The device according to claim 1, in which the through bore is tapered and of reducing area in the exhaust flow direction. 
     
     
       3. The device according to claim 2, in which the through bore is of circular cross-section and defines an included angle of between 20 and 30 degrees. 
     
     
       4. The device according to claim 1, in which the disrupter means comprises a series of members having tapered through bores positioned in the path of incoming exhaust gases, with each member having a bore of area less than the flow area of exhaust gases incident on it. 
     
     
       5. The device according to claim 1, in which the disrupter means is coated with a thermal ablative material. 
     
     
       6. The device according to claim 1, in which the internal surface of the container is coated with thermal ablative material. 
     
     
       7. A dissipator device for connection to a rocket exhaust, comprising: an elongated container closed at its opposite longitudinal ends and having an inlet at an intermediate point in its length for connection to a rocket exhaust, the container having a plurality of exhaust orifices along its length of smaller dimensions than the inlet for exhaust flow out of the container in a plurality of different directions;   a solid deflector surface in the container positioned opposite the inlet for deflecting incoming gas flow out of the incoming flow directions and into opposite directions normal to the incoming flow direction and towards the opposite ends of the container; and   a disrupter member mounted in the container in the path of incoming gas flow between the inlet and the deflector surface for reducing the pressure of exhaust gases downstream of the disrupter member, the disrupter member having a central through bore aligned with the inlet, the through bore having an inlet opening closest to the inlet which is spaced from the exhaust inlet and has an area less than the cross-sectional area of the exhaust flow at the disrupter member, and being shaped for restricting the exhaust gas flow and directing it to flow both through and around the disrupter member.